CN109747862A - Method for manufacturing aircraft fuselage - Google Patents
Method for manufacturing aircraft fuselage Download PDFInfo
- Publication number
- CN109747862A CN109747862A CN201811302735.4A CN201811302735A CN109747862A CN 109747862 A CN109747862 A CN 109747862A CN 201811302735 A CN201811302735 A CN 201811302735A CN 109747862 A CN109747862 A CN 109747862A
- Authority
- CN
- China
- Prior art keywords
- isolation board
- paillon
- airframe structure
- isolation
- conductor circuit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 15
- 238000002955 isolation Methods 0.000 claims abstract description 115
- 239000004020 conductor Substances 0.000 claims abstract description 29
- 239000011888 foil Substances 0.000 claims description 9
- 238000005192 partition Methods 0.000 claims description 8
- 239000012777 electrically insulating material Substances 0.000 claims description 7
- 238000007641 inkjet printing Methods 0.000 claims description 7
- 239000002245 particle Substances 0.000 claims description 6
- 238000007639 printing Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 239000000853 adhesive Substances 0.000 description 3
- 238000004378 air conditioning Methods 0.000 description 3
- 239000006260 foam Substances 0.000 description 3
- 229920000715 Mucilage Polymers 0.000 description 2
- 239000002390 adhesive tape Substances 0.000 description 2
- 238000000149 argon plasma sintering Methods 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000007767 bonding agent Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000007645 offset printing Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/066—Interior liners
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
- B64C1/403—Arrangement of fasteners specially adapted therefor, e.g. of clips
- B64C1/406—Arrangement of fasteners specially adapted therefor, e.g. of clips in combination with supports for lines, e.g. for pipes or cables
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0625—Environmental Control Systems comprising means for distribution effusion of conditioned air in the cabin
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Laminated Bodies (AREA)
- Manufacturing Of Printed Wiring (AREA)
- Insulating Bodies (AREA)
Abstract
A kind of method for manufacturing aircraft fuselage (1) has been illustrated and described.Purpose for simplifying and speeding up the aircraft fuselage manufacture is realized by following steps :-airframe structure (3) are provided, the airframe structure is around inside cabin (5) out and has the inside (7) for being directed toward the inside cabin (5)；The isolation board (19) for the airframe structure (3) to be isolated is provided, wherein the isolation board (19) has inner surface (21) and outer surface (23)；The paillon (31) for being provided with conductor circuit (29) is provided；The paillon (31) are fixed on the inner surface (21) of the isolation board (19)；And the isolation board (19) is arranged on the inside (7) of the airframe structure (3).
Description
Technical field
Method, especially one kind that the present invention relates to a kind of for manufacturing aircraft fuselage are used to manufacture with integrated electrical system
The method of the aircraft fuselage of system.Other aspects of the present invention are related to a kind of isolation board and one for aircraft fuselage to be isolated
The such aircraft of kind.
Background technique
From the prior art it is known that first with felt pad lining airframe structure during manufacturing aircraft fuselage
Inside, and then various aerocraft systems are installed on these felt pads, such as electrical harness, air-conditioning system etc..For this purpose,
The bracket of primary structure (such as skeleton, stringers) line of rabbet joint must be passed through to be introduced into these felt pads.Then in these felt pads
With the interior cabin wall with secondary puigging fixed in system.But this frame mode need it is with high costs worked
Journey, because felt pad and system will be disposed and be adjusted manually.
Summary of the invention
Therefore the purpose of the present invention is simplify and speed up the manufacturing process of aircraft fuselage.
The purpose is realized by the method having follow steps:
Airframe structure, especially fuselage wall are provided first, and the airframe structure is around inside cabin out and has the interior of direction inside cabin
Side.The airframe structure preferably has exterior skin and the skeleton extended along circumferential direction and the stringers extendd in the longitudinal direction,
It is used to support the exterior skin on inside.
It also provides for the isolation board for airframe structure isolation cold and noise.The isolation board is preferably by heat-insulated and sound insulation
Material, such as rigid foam is made.The isolation board has the inner surface and the outer surface and is preferably bent such that inner surface
Concave and outer surface is in convex.
Furthermore the paillon for being provided with conductor circuit and/or switch element is also provided.These conductor circuits are preferably formed as flying
The electrical system of row device, the electrical system be arranged for being contained in aircraft fuselage machinery space bulkhead and airframe structure it
Between.Here, these conductor circuits can include all electrical systems and integrated switching circuitry.
These paillons are fixed, are for example pasted on the inner surface of isolation board.As an alternative, isolation board can also be fixed to
Inner surface on after just for paillon assemble conductor circuit.
Then the isolation board for being provided with these paillons is placed on the inside of airframe structure.As an alternative, it can also incite somebody to action
Other structures element or cabin elements assemble electricity before being installed in fuselage for it and print paillon.
In this way it is possible to largely prefabricated isolation board or cabin elements, and install needed for electrical system
Time-consuming handwork can be reduced to minimum, so as to significantly it is simplified, accelerate and standardize the manufacturing method.
According to a kind of preferred embodiment, on the inside that the isolation board is arranged to the airframe structure it
Afterwards, cabin wall section is placed on the inside of the airframe structure so that the isolation board the airframe structure with
Extend between the cabin wall section.In this way, the additional electrical system of installation is not needed before disposing cabin wall section
System, such as harness.
According to another preferred embodiment, provides the paillon for being provided with conductor circuit in the following manner, make
It obtains and prints out conductor circuit to the paillon blank being formed of an electrically insulating material.It can be uncomplicated and quick by printed conductor circuit
Complicated electrical system is realized on paillon in ground.
Here it is preferred, in particular, that printed by ink-jet printing apparatus, wherein by the particle of conductive material and excellent
There are also the particles of electrically insulating material to be applied on paillon blank and then be fixed in a predetermined pattern, especially carry out for choosing
Connection and hardening.For example it can be attached and harden by laser sintering device.It ink jet printing and laser sintered contributes to
The effective ways of printed conductor circuit.Instead of ink-jet printing apparatus, also can be used offset printing appts, screen printer or
Gravure apparatus prints paillon blank.
Herein it is also preferred that applying after the printing by the foil being made of insulating material, being preferably pasted onto foil
That side that piece has printed.The foil is for protecting conductor circuit and avoiding contact with conductor circuit.
According to another preferred embodiment, multiple isolation boards are provided and pieced together after the fixation paillon every
From hardened structure, so that the inner surface of the single isolation board and the paillon fixed thereon form common surface,
In then the conductor circuit of respective foils is connected, such as pass through plug-in connector.This split can be with or airframe structure
Except just carried out or can also just have been carried out within airframe structure, such as isolation board is being placed in airframe structure
When on inside.In this way, isolation board can simply and quickly be combined and can equably covers machine
The major part of body structure.
According to a kind of embodiment of alternative, multiple isolation boards are provided and are pieced together isolation board before fixed paillon
Structure, so that the inner surface of single isolation board forms common surface, wherein the common foil of conductor circuit then will be provided with
Piece is fixed on the common surface.Common paillon preferably extends on entire common surface, but at least extends multiple
Isolation board.In this way, it can mostly be provided except airframe structure and isolation board is arranged in airframe structure, and
Thus it is largely simplified and accelerates.
Here it is preferred, in particular, that the partition plate structure is supported on when carrying out split outside the airframe structure
It supports on trolley (St ü tztrolleys), and pushes it into the airframe structure by the support trolley to be placed in
It states on the inside of airframe structure.This support trolley, which significantly simplifies, to be provided partition plate structure and is placed in fuselage knot
In structure.
It is also especially preferred that the isolation board has attachment device, it can will be adjacent by these attachment devices
Isolation board is connected to each other.This attachment device for example can be connector arrangement, wherein by protrusion on isolation board or convex
Edge is joined in the recess or eyelet of another isolation board, in some instances it may even be possible to more than the skeleton of airframe structure.Other realities of attachment device
Example is magic tape or adhesive, such as mucilage materials or adhesive tape.
According to another preferred embodiment, isolation board has air pipeline or inside it for the recessed of air pipeline
Mouthful.This air pipeline may, for example, be the pipe or hose of air-conditioning system, such as 21 air pipeline of ATA.In this way,
These air pipelines are integrated into isolation board, and without being specially arranged and installing, thus simplify and speed up aircraft machine
The manufacture of body.
According to also another preferred embodiment, isolation board in horizontal longitudinal direction, be transversely to the machine direction the circumferential direction in direction
Direction and being transversely to the machine direction between direction and the thickness direction of circumferential direction extends.The size of the isolation board in a longitudinal direction with
The distance between two adjacent skeletons of airframe structure are corresponding.It can be fixed between every two skeleton in this way
One isolation board.
Preferably, isolation boards multiple in tandem along circumferential direction, wherein for example the first isolation board extended floor segment,
Two isolation boards extended aircraft window section, and third isolation board extended luggage carrier section, and the 4th isolation board extended ceiling section.Pass through
Isolation board can be used as general part to produce by this mode on a large scale.
Another aspect of the present invention relates to a kind of isolation board, which is used to be aircraft fuselage or affiliated airframe structure
It is isolated, especially isolation cold and noise.The isolation board is formed by insulating materials, such as rigid foam.The isolation board is in water
Flat longitudinal direction is transversely to the machine direction the circumferential direction in direction and is transversely to the machine direction between direction and the thickness direction of circumferential direction
Extend.The isolation board is preferably bent such that inner surface is configured to spill and outer surface is configured to convex.The isolation board is vertical
Size on direction is preferably corresponding with the distance between two adjacent skeletons of the airframe structure of aircraft fuselage, this flies
Row device fuselage should be isolated by the isolation board.The isolation board has the inner surface and the outer surface on the contrary in a thickness direction.
The isolation board is configured on the inside for being fixed on the airframe structure of aircraft fuselage with outer surface.It fixes on an internal surface
Be provided with, be especially printed with the paillon of conductor circuit.
According to a kind of preferred embodiment, which has attachment device, can should by these attachment devices
Isolation board is connected with another isolation board.This attachment device for example can be connector arrangement, wherein can will be on isolation board
Protrusion or flange be joined in the recess or eyelet of another isolation board.Other examples of attachment device are magic tape or bonding
Agent, such as mucilage materials or adhesive tape.
According to another preferred embodiment, isolation board has air pipeline or inside it for the recessed of air pipeline
Mouthful.This air pipeline can especially air-conditioning system pipe or hose, such as 21 air pipeline of ATA.In this way,
These air pipelines are integrated into isolation board, and without being specially arranged, thus, it is possible to simplify and speed up aircraft fuselage
Isolation.
Another aspect of the present invention relates to a kind of aircraft, such as aircraft or helicopter.The aircraft includes before
The aircraft fuselage or the isolation board according to one of aforementioned embodiments for stating the embodiment manufacture of method.It ties before
It closes feature and advantage mentioned by this method and the isolation board and is naturally also suitable for this aircraft.
Brief description
The embodiment of the present invention is described in detail by attached drawing below.Attached drawing is shown:
Fig. 1 shows the perspective view of the airframe structure of embodiment according to the present invention,
Fig. 2 shows the perspective view of row's isolation board of embodiment according to the present invention,
Fig. 3 shows the schematic diagram of the method for manufacturing the paillon for being provided with conductor circuit,
Fig. 4 shows the perspective view for being fixed with the isolation board of the paillon with conductor circuit thereon,
Fig. 5 shows the perspective view for the partition plate structure being fixed on support trolley,
Fig. 6 shows the cross-section details figure for two isolation boards being placed on the inside of airframe structure, the two isolation boards warp
It is connected with each other by attachment device, and
Fig. 7 shows the distribution in the particular range of the section view and isolation board of aircraft fuselage in circumferential direction.
Specific embodiment
Method according to the present invention for manufacturing aircraft fuselage 1, first offer airframe structure 3, such as Fig. 1 institute
Show, the airframe structure is around inside cabin 5 out and has the inside 7 for being directed toward inside cabin 5.Airframe structure 3 has exterior skin 9, Yi Jiyan
The skeleton 13 of the extension of circumferential direction 11 and the along the longitudinal direction stringers 17 of 15 extensions, the exterior skin 9 being used to support on inside 7.
As shown in Fig. 2, also providing multiple isolation board 19 made of rigid foam.Isolation board 19 has 21 He of inner surface
Outer surface 23 and it is bent such that inner surface 21 is configured to spill and outer surface 23 is configured to convex.Isolation board 19 is in level
Longitudinal direction 15, the circumferential direction 11 for being transversely to the machine direction direction 15 and the thickness for being transversely to the machine direction direction 15 and circumferential direction 11
Extend between direction 25.These sizes of single isolation board 19 on longitudinal direction 15 are two adjacent with airframe structure 3
The distance between skeleton 13 is corresponding, so as to fix an isolation board 19 between every two skeleton 13.In addition, isolation board
19 also have air pipeline 27, such as ATA21 air pipeline inside it.
Further it is provided that being provided with the paillon 31 of conductor circuit 29.As shown in Figure 3a and 3b shown, it produces in the following manner
It is provided with the paillon 31 of conductor circuit 29, so that printing out conductor circuit 29 to the paillon blank 33 being formed of an electrically insulating material.
It is printed by ink-jet printing apparatus 35, wherein in a predetermined pattern by the particle of the particle of conductive material and electrically insulating material
It is applied on paillon blank 33, and is then fixed by laser sintering device 37, that is, is connected with each other and is hardened.?
This, precut paillon block 39 can be introduced ink-jet printing apparatus 35 from stacking 41 as shown in Figure 3a can also be by idler wheel 45
By continuous 43 debatching of paillon, it is conducted across ink-jet printing apparatus 35 and then again wraps around another idler wheel 47
On, as shown in Figure 3b.After the printing, the foil 49 that is formed of an electrically insulating material is pasted onto having printed for paillon 31
That side.
As shown in figure 4, paillon 31 is fixed, is for example pasted on the inner surface 21 of isolation board 19.Then foil will be provided with
The isolation board 19 of piece 31 is placed on the inside 7 of airframe structure 3.
In the embodiment shown, single isolation board 19 is pieced together into partition plate structure 51 before fixed paillon 31,
Especially as follows: the inner surface 21 of these single isolation boards 19 forms common surface 53.Then conductor will be provided with
The common paillon 55 of circuit 29 is fixed on common surface 53.Here, common paillon 55 extended common total surface
53.As shown in figure 5, partition plate structure 51 is supported on support trolley 57, and is borrowed when carrying out split outside airframe structure 3
Support trolley 57 is helped to push it into airframe structure 3 to be placed on the inside 7 of airframe structure 3.
However, the embodiment shown in, it is also possible to: paillon 31 is fixed on before split isolation board 19
On isolation board, that is to say, that single isolation board 19 is made to be pieced together partition plate structure 51, mode after fixed paillon 31
It, thus then will be adjacent to make inner surface 21 and the paillon 31 fixed thereon of single isolation board 19 form common surface 53
Paillon 31 conductor circuit 29 be connected, for example pass through plug-in connector.This split can with or except airframe structure 3 just
It has carried out or can also just have been carried out within airframe structure 3, such as be placed in airframe structure 3 by isolation board 19
When on side 7.
In order to simplify the split of these isolation boards 19, these isolation boards 19 can have attachment device 59, by these companies
Adjacent isolation board 19 can be connected by connection device.As shown in fig. 6, these attachment devices 59 for example can be plug connection dress
Set, wherein by isolation board 19 protrusion 61 or flange engage into the recess 63 or eyelet of another adjacent isolation board 19.
This attachment device 59 can even extend the skeleton 13 of airframe structure 3.
After on the inside 7 that isolation board 19 is arranged to airframe structure 3, cabin wall section 65 is placed in airframe structure
On 3 inside 7, so that isolation board 19 extends between airframe structure 3 and cabin wall section 65, as shown in Figure 7a.Here, multiple
Isolation board 19 along circumferential direction 11 each other in tandem, as shown in Figure 7b, wherein the first isolation board 67 extended floor segment 69,
Two isolation boards 71 extended aircraft window section 73, and third isolation board 75 extended luggage carrier section 77, and the 4th isolation board 79 extended day
Card section 81.
Claims (15)
1. method of the one kind for manufacturing aircraft fuselage (1), the method have follow steps:
It provides airframe structure (3), the airframe structure is around inside cabin (5) out and has the inside for being directed toward the inside cabin (5)
(7)；
The isolation board (19) for the airframe structure (3) to be isolated is provided, wherein the isolation board (19) has inner surface (21)
With outer surface (23)；
The paillon (31) for being provided with conductor circuit (29) is provided；
The paillon (31) are fixed on the inner surface (21) of the isolation board (19)；And
The isolation board (19) is arranged on the inside (7) of the airframe structure (3).
2. according to the method described in claim 1, wherein in the institute that the isolation board (19) is arranged to the airframe structure (3)
After stating on inside (7), cabin wall section (65) is placed on the inside (7) of the airframe structure (3), so that described
Isolation board (19) extends between the airframe structure (3) and the cabin wall section (65).
3. method according to claim 1 or 2, wherein providing the institute for being provided with conductor circuit (29) in the following manner
Paillon (31) are stated, so that printing out conductor circuit (29) to the paillon blank (33) being formed of an electrically insulating material.
4. according to the method described in claim 3, wherein, being printed by ink-jet printing apparatus (35), wherein by conduction material
The particle of material and the particle of electrically insulating material are applied on the paillon blank (33) in a predetermined pattern and are then consolidated
It is fixed.
5. the method according to claim 3 or 4, wherein after said printing, applied in the printed side of the paillon (31)
Add foil (49).
6. method according to claim 1 to 5, wherein providing multiple isolation boards (19) and in the fixation paillon
(31) after pieced together partition plate structure (51) so that the inner surface (21) of the single isolation board (19) with thereon
The fixed paillon (31) forms common surface (53), wherein the then conductor circuit (29) phase of respective foils (31)
Even.
7. method according to claim 1 to 5, wherein providing multiple isolation boards (19) and in the fixation paillon
(31) partition plate structure (51) are pieced together before, so that the inner surface (21) of the single isolation board (19) is formed altogether
Same surface (53), wherein the common paillon (55) for being provided with conductor circuit (29) is then fixed on the common surface
(53) on.
8. method according to claim 6 or 7, wherein when the airframe structure (3) carries out split outside, will it is described every
It is supported in support trolley (57) from hardened structure (51), and pushes it into the airframe structure by the support trolley (57)
(3) to be placed on the inside (7) of the airframe structure (3) in.
9. the method according to one of claim 6 to 8, wherein the isolation board (19) has attachment device (59), by
Adjacent isolation board (19) can be connected with each other by these attachment devices.
10. according to claim 1 to method described in one of 9, wherein the isolation board (19) has air pipeline inside it
(27) or be used for air pipeline (27) recess.
11. according to claim 1 to method described in one of 10, wherein the isolation board (19) is in longitudinal direction (15), circumferential direction
Extend between direction (11) and thickness direction (25), wherein size of the isolation board (19) on longitudinal direction (15) with it is described
The distance between two adjacent skeletons (13) of airframe structure (3) are corresponding.
12. one kind is used to be isolated the isolation board (19) of aircraft fuselage (1),
Wherein the isolation board (19) extends between longitudinal direction (15), circumferential direction (11) and thickness direction (25),
Wherein the isolation board (19) has inner surface (21) and outer surface (23) on the contrary on thickness direction (25),
Wherein the isolation board (19) is configured for being fixed on the machine of the aircraft fuselage (1) with the outer surface (23)
On the inside (7) of body structure (3), and
The paillon (31) for being provided with conductor circuit (29) is wherein fixed on the inner surface (21).
13. isolation board according to claim 12, wherein the isolation board (19) has attachment device (59), by these
The isolation board (19) can be connected by attachment device with another isolation board (19).
14. isolation board according to claim 12 or 13, wherein the isolation board (19) has air pipeline inside it
(27) or be used for air pipeline (27) recess.
15. a kind of aircraft, the aircraft fuselage (1) of one of described with good grounds claim 1 to 11 of flying instrument manufacture, or
With isolation board (19) described according to claim 1 one of 2 to 14.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102017125763.2 | 2017-11-03 | ||
| DE102017125763.2A DE102017125763A1 (en) | 2017-11-03 | 2017-11-03 | Method for producing an aircraft fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109747862A true CN109747862A (en) | 2019-05-14 |
Family
ID=66179241
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811302735.4A Pending CN109747862A (en) | 2017-11-03 | 2018-11-02 | Method for manufacturing aircraft fuselage |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US11708144B2 (en) |
| CN (1) | CN109747862A (en) |
| DE (1) | DE102017125763A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102017125763A1 (en) * | 2017-11-03 | 2019-05-09 | Airbus Operations Gmbh | Method for producing an aircraft fuselage |
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Also Published As
| Publication number | Publication date |
|---|---|
| US11708144B2 (en) | 2023-07-25 |
| DE102017125763A1 (en) | 2019-05-09 |
| US20190135404A1 (en) | 2019-05-09 |
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Application publication date: 20190514 |